The present disclosure relates to a water tank configured for operation in an aircraft (50). The tank comprises a rigid tank shell (110), and a pressure compensation mechanism (120) configured to equalise a pressure inside of the rigid tank shell with an environment. The pressure compensation mechanism comprises a shutoff member (122) configured to move between a closed position, a first open position allowing air to enter the rigid tank shell and a second open position allowing air to leave the rigid tank shell.
PRESSURELESS WATER TANK FOR OPERATION IN AN AIRCRAFT, AIRCRAFT SECTION AND AIRCRAFT HAVING A WATER TANK
DRUCKLOSER WASSERTANK FÜR DEN BETRIEB IN EINEM FLUGZEUG, FLUGZEUGABSCHNITT UND FLUGZEUG MIT WASSERTANK
RÉSERVOIR D'EAU SANS PRESSION POUR FONCTIONNEMENT DANS UN AÉRONEF, SECTION D'AÉRONEF ET AÉRONEF COMPORTANT UN RÉSERVOIR D'EAU
2024-03-06
Patent
Electronic Resource
English
IPC: | B64D Ausrüstung für Flugzeuge , EQUIPMENT FOR FITTING IN OR TO AIRCRAFT |
Water tank configured for operation in aircraft, aircraft section and aircraft
European Patent Office | 2024
|